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GOE 228 (MVA H.38) AIRFOIL (goe228-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 228 (MVA H.38) AIRFOIL (goe228-il)
Reynolds number: 200,000
Max Cl/Cd: 70.64 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe228-il-200000.txt
Download as CSV file: xf-goe228-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 228 (MVA H.38) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250   0.0029   0.09300   0.08933  -0.1245   0.9386   0.0886
 -10.000   0.0240   0.09101   0.08733  -0.1222   0.9330   0.0896
  -9.750  -0.1748   0.04915   0.04496  -0.1589   0.9075   0.0587
  -9.500  -0.1801   0.04404   0.03953  -0.1651   0.8975   0.0585
  -9.250  -0.1694   0.03924   0.03415  -0.1714   0.8910   0.0588
  -9.000  -0.1450   0.03513   0.02959  -0.1759   0.8878   0.0596
  -8.750  -0.1324   0.03327   0.02760  -0.1754   0.8785   0.0602
  -8.500  -0.1033   0.03124   0.02541  -0.1771   0.8745   0.0611
  -8.250  -0.0712   0.02944   0.02344  -0.1790   0.8715   0.0624
  -8.000  -0.0508   0.02835   0.02219  -0.1787   0.8633   0.0638
  -7.750  -0.0204   0.02681   0.02036  -0.1801   0.8584   0.0656
  -7.500   0.0132   0.02535   0.01855  -0.1817   0.8549   0.0670
  -7.250   0.0374   0.02408   0.01713  -0.1816   0.8475   0.0682
  -7.000   0.0659   0.02290   0.01595  -0.1820   0.8417   0.0703
  -6.750   0.0986   0.02196   0.01492  -0.1829   0.8376   0.0731
  -6.500   0.1245   0.02133   0.01417  -0.1827   0.8297   0.0757
  -6.250   0.1542   0.02031   0.01304  -0.1831   0.8235   0.0783
  -6.000   0.1865   0.01931   0.01207  -0.1839   0.8191   0.0821
  -5.750   0.2116   0.01884   0.01156  -0.1835   0.8097   0.0868
  -5.500   0.2430   0.01790   0.01063  -0.1843   0.8037   0.0935
  -5.250   0.2716   0.01727   0.00999  -0.1846   0.7957   0.1023
  -5.000   0.3023   0.01658   0.00932  -0.1854   0.7880   0.1157
  -4.750   0.3336   0.01596   0.00875  -0.1862   0.7807   0.1360
  -4.500   0.3634   0.01533   0.00824  -0.1869   0.7714   0.1694
  -4.250   0.3953   0.01482   0.00797  -0.1880   0.7638   0.2446
  -4.000   0.4237   0.01483   0.00797  -0.1879   0.7536   0.2863
  -3.750   0.4532   0.01490   0.00790  -0.1879   0.7445   0.3118
  -3.500   0.4818   0.01495   0.00789  -0.1878   0.7344   0.3317
  -3.250   0.5098   0.01504   0.00788  -0.1877   0.7235   0.3482
  -2.750   0.5662   0.01493   0.00763  -0.1874   0.7018   0.3707
  -2.500   0.5942   0.01493   0.00754  -0.1873   0.6904   0.3820
  -2.250   0.6230   0.01487   0.00737  -0.1873   0.6798   0.3923
  -2.000   0.6502   0.01490   0.00729  -0.1871   0.6672   0.4026
  -1.750   0.6775   0.01486   0.00722  -0.1869   0.6554   0.4108
  -1.500   0.7061   0.01492   0.00711  -0.1870   0.6450   0.4211
  -1.250   0.7327   0.01495   0.00712  -0.1867   0.6333   0.4303
  -1.000   0.7602   0.01507   0.00712  -0.1866   0.6224   0.4414
  -0.750   0.7877   0.01515   0.00713  -0.1865   0.6126   0.4516
  -0.500   0.8143   0.01526   0.00719  -0.1863   0.6017   0.4620
  -0.250   0.8419   0.01537   0.00722  -0.1863   0.5928   0.4697
   0.000   0.8686   0.01550   0.00729  -0.1862   0.5832   0.4796
   0.250   0.8961   0.01565   0.00740  -0.1862   0.5751   0.4882
   0.500   0.9226   0.01581   0.00751  -0.1860   0.5663   0.4989
   0.750   0.9505   0.01601   0.00765  -0.1860   0.5590   0.5090
   1.000   0.9760   0.01617   0.00785  -0.1857   0.5506   0.5214
   1.250   1.0039   0.01641   0.00798  -0.1858   0.5436   0.5364
   1.500   1.0292   0.01662   0.00825  -0.1854   0.5360   0.5506
   1.750   1.0555   0.01682   0.00845  -0.1852   0.5292   0.5666
   2.000   1.0830   0.01710   0.00867  -0.1852   0.5232   0.5847
   2.250   1.1077   0.01731   0.00895  -0.1848   0.5164   0.6041
   2.500   1.1342   0.01755   0.00914  -0.1846   0.5104   0.6252
   2.750   1.1598   0.01781   0.00941  -0.1843   0.5044   0.6455
   3.000   1.1838   0.01800   0.00968  -0.1837   0.4980   0.6649
   3.250   1.2100   0.01822   0.00987  -0.1835   0.4926   0.6845
   3.500   1.2355   0.01848   0.01015  -0.1832   0.4875   0.7042
   3.750   1.2589   0.01869   0.01045  -0.1826   0.4821   0.7242
   4.000   1.2838   0.01889   0.01067  -0.1822   0.4771   0.7453
   4.250   1.3113   0.01915   0.01089  -0.1823   0.4724   0.7676
   4.500   1.3311   0.01931   0.01122  -0.1810   0.4671   0.7926
   4.750   1.3519   0.01940   0.01143  -0.1797   0.4621   0.8344
   5.000   1.3740   0.01945   0.01153  -0.1787   0.4579   1.0000
   5.250   1.4020   0.01989   0.01190  -0.1791   0.4539   1.0000
   5.500   1.4251   0.02027   0.01233  -0.1787   0.4497   1.0000
   5.750   1.4500   0.02065   0.01270  -0.1785   0.4458   1.0000
   6.000   1.4763   0.02103   0.01304  -0.1786   0.4424   1.0000
   6.250   1.5056   0.02147   0.01337  -0.1792   0.4392   1.0000
   6.500   1.5284   0.02194   0.01389  -0.1787   0.4360   1.0000
   6.750   1.5496   0.02238   0.01442  -0.1779   0.4326   1.0000
   7.000   1.5727   0.02281   0.01488  -0.1775   0.4293   1.0000
   7.250   1.5974   0.02322   0.01528  -0.1773   0.4263   1.0000
   7.500   1.6243   0.02364   0.01566  -0.1775   0.4236   1.0000
   7.750   1.6524   0.02416   0.01615  -0.1779   0.4208   1.0000
   8.000   1.6673   0.02467   0.01680  -0.1761   0.4175   1.0000
   8.250   1.6851   0.02514   0.01737  -0.1747   0.4141   1.0000
   8.500   1.7062   0.02560   0.01787  -0.1740   0.4111   1.0000
   8.750   1.7300   0.02603   0.01830  -0.1737   0.4084   1.0000
   9.000   1.7577   0.02646   0.01871  -0.1740   0.4058   1.0000
   9.250   1.7791   0.02705   0.01937  -0.1734   0.4032   1.0000
   9.500   1.7887   0.02768   0.02015  -0.1708   0.4005   1.0000
   9.750   1.8011   0.02829   0.02088  -0.1686   0.3976   1.0000
  10.000   1.8174   0.02886   0.02153  -0.1671   0.3949   1.0000
  10.250   1.8376   0.02936   0.02208  -0.1663   0.3924   1.0000
  10.500   1.8633   0.02973   0.02245  -0.1664   0.3898   1.0000
  10.750   1.8816   0.03032   0.02309  -0.1653   0.3865   1.0000
  11.000   1.8775   0.03127   0.02423  -0.1609   0.3830   1.0000
  11.250   1.8809   0.03199   0.02506  -0.1576   0.3785   1.0000
  11.500   1.8969   0.03228   0.02533  -0.1562   0.3739   1.0000
  11.750   1.9105   0.03290   0.02598  -0.1546   0.3697   1.0000
  12.000   1.9042   0.03425   0.02754  -0.1506   0.3659   1.0000
  12.250   1.9074   0.03529   0.02869  -0.1479   0.3616   1.0000
  12.500   1.9204   0.03585   0.02926  -0.1464   0.3573   1.0000
  12.750   1.9283   0.03682   0.03030  -0.1444   0.3529   1.0000
  13.000   1.9181   0.03877   0.03245  -0.1407   0.3482   1.0000
  13.250   1.9196   0.04009   0.03387  -0.1384   0.3431   1.0000
  13.500   1.9331   0.04076   0.03449  -0.1372   0.3379   1.0000
  13.750   1.9184   0.04346   0.03745  -0.1339   0.3332   1.0000
  14.000   1.9140   0.04553   0.03964  -0.1316   0.3276   1.0000
  14.250   1.9213   0.04674   0.04083  -0.1302   0.3217   1.0000
  14.500   1.9051   0.05022   0.04456  -0.1277   0.3159   1.0000
  14.750   1.9025   0.05256   0.04697  -0.1261   0.3094   1.0000
  15.000   1.8927   0.05585   0.05041  -0.1245   0.3024   1.0000
  15.250   1.8825   0.05934   0.05401  -0.1232   0.2943   1.0000
  15.500   1.8684   0.06352   0.05833  -0.1220   0.2858   1.0000
  15.750   1.8588   0.06726   0.06211  -0.1211   0.2766   1.0000
  16.000   1.8364   0.07292   0.06796  -0.1205   0.2666   1.0000
  16.250   1.8165   0.07839   0.07352  -0.1200   0.2552   1.0000
  16.500   1.7943   0.08425   0.07944  -0.1198   0.2424   1.0000
  16.750   1.7712   0.09035   0.08556  -0.1198   0.2287   1.0000
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